Simulation of transient augmenting work stability for a turbofan engine

The stage-by-stage cell control volume modeling technique which was used in the compression system is applied to a mixed exhaust turbofan engine with afterburner. The model is combined with the engine components matching technology in this paper. The explicit MacCormack two-step difference schemes and characteristic line method were used to simulate the process of transient augmenting engine stability and test the capability of surge elimination before adjusting the fan inlet guide vanes and after adjusting the fan inlet guide vanes in the condition of flow disturbances. The influence of the engine performance by the stator vanes adjusting was studied as well. The simulation results showed that the qualitative investigation of numerical model meets the project requirements, the numerical algorithm used is efficient. It is an effective means of improve stability of the aeroengine to regulate the fan inlet guide vanes. The positive regulation of fan inlet guide blades causes the engine specific thrust down, but the specific fuel consumption increases. The fan which was in surge recovers faster by increasing the fuel cutoff rate in the afterburner.